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Completed Tabulation in the United States of Tests of 24 Airfoils at High Mach Numbers (Derived from Interrupted Work at Guidonia, Italy in the 1.31- by 1.74-Foot High-Speed Tunnel)Two-dimensional data were obtained in Mach range of from 0.40 to 0.94 and Reynolds Number range of (3.4 - 4.2) X 10 Degrees. Results indicate that thickness ratio is dominating shape parameter at high Mach numbers and that aerodynamic advantages are attainable by using thinnest possible sections. Effects of jet boundaries, Reynolds Number, and Data presented are free from jet-boundary and humidity effects.
Document ID
19930092764
Acquisition Source
Legacy CDMS
Document Type
Other - NACA Wartime Report
External Source(s)
hdl:100.2/ADA800596
Authors
Ferri, Antonio (National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Date Acquired
September 6, 2013
Publication Date
June 1, 1945
Subject Category
Aerodynamics
Report/Patent Number
NACA-ACR-L5E21
NACA-WR-L-143
Accession Number
93R22054
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
AIR FLOW VELOCITY, HIGH - SUBSONIC
AIRFOILS - NACA 0009-63 - CHAR , MOMENTS & ORDINATES
AIRFOILS - NACA 0006-64 - CHAR , MOMENTS & ORDINATES
AIRFOILS - DAVIS - CHAR , MOMENTS & ORDINATES LAMINAR-FLOW
AIRFOILS - NACA 0008-34 - CHAR , MOMENTS & ORDINATES
AIRFOILS - NACA 0006T - CHAR , MOMENTS & ORDINATES
AIRFOILS - THICKNESS
AIRFOILS - CHARACTERISTICS - EFFECT OF COMPRESSIBILITY
AIRFOILS - NACA 0009-64 - CHAR , MOMENTS & ORDINATES
AIRFOILS - NACA 0006-34 - CHAR , MOMENTS & ORDINATES

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